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EngineCycles - Liquid Rocket Engine Cycles AAE 539:...

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Liquid Rocket Engine Cycles AAE 539: Advanced Rocket Propulsion Spring 2007
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Pressure Fed Cycle Advantages Simple, reliable design No turbo pump Disadvantages •Limited to small t b , low thrust Only limited throttling Tanks must withstand high pressure Tank bladders might be required Used in space vehicle attitude control, apogee engines Fuel Oxid. He, N 2 High Pressure Gas Source
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Gas Generator Cycle (GG) Open Cycle – Turbine exhaust doesn’t go thru main chamber GG burns non-stoichiometric to eliminate turbine cooling Advantages Fairly simple Wide thrust operating range Disadvantages •Turbine exhaust gives low I sp – and effective loss in performance Gas generator required RS-27, MA-5, STME, Titan
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Gas Generator Cycle Rocket Engine Fuel Turbine Ox. Turbine
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Production GG Cycle Engines ENGINE HM7B Viking VC HM60 LR87 LR91 MA-5A Booster MA-5A Sustainer RS-27A Contractor SEP SEP SEP Aerojet Aerojet Rocketdyne Rocketdyne Rocketdyne Stage Ariane 4 3nd Stage Ariane 4 1st Stage Ariane 5 1st Stage Titan IV 1st Stage Titan IV 2nd Stage Atlas II 1st Stage Booster Atlas II 1st Stage Sustainer Delta II/III 1st Stage Propellants LOX/LH2 N204 / UH25 LOX/LH2 N204 / Aerozine 50 N204 / Aerozine 50 LOX/RP1 LOX/RP1 LOX/RP1 Thrust Sea Level, lbf -- 152,000 198,000 447,300 -- 429,500 60,500 199,945 Vacuum, lbf 14,100 171,000 250,500 552,500 106,200 85,000 237,067 Throttle Fixed Fixed Fixed Fixed Fixed Fixed 45% to 100% Fixed Specific Impulse Sea Level, sec -- 248.5 340.0 246.1 263.3 265.0 220.0 254.8 Vacuum, sec 445.1 278.4 431.0 304.0 318.0 308.0 302.1 Mixture Ratio 4.77 1.70 5.30 1.91 1.86 2.25 2.27 2.245 Chamber Pressure Nozzle Stagnation, psia 521.8 875.7 1646.6 827.0 827.0 719.0 736.0 654.8 Area Ratio 62.5 10.48 45 15 49.2 8 25 12 Dry Weight, lbs 341 1953 3571 4583 1284 3336 1035 2527.9 Thrust/Weight (Sea Level) 77.8 55.4 97.6 128.7 58.5 79.1 Thrust/Weight (Vacuum) 41.3 87.5 70.1 120.6 82.7 0.0 82.1 93.8
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ENGINE MC-1 Vulcain 2 (HM60) RS-68 XRS-2200 Contractor MSFC SEP Rocketdyne Rocketdyne Stage X-34 Ariane 5 1st Stage Delta IV 1st Stage X-33 Propellants LOX/Kerosene LOX/LH2 LOX/LH2 LOX/LH2 Thrust Sea Level, lbf 40,532 223,000 663,232 204,400 Vacuum, lbf 63,939 303,507 745,000 266,200 Throttle Fixed Fixed 60% to 100% 50% @ 4.75 MR +/- 15 % Differential Throttling Specific Impulse Sea Level, sec 199.0 318.0 365.0 339.0 Vacuum, sec 314.0 433.0 410.0 436.5 Mixture Ratio 2.17 6.10 6.00 5.50 Chamber Pressure Nozzle Stagnation, psia 633 1736.4 1410 857.0 Area Ratio 30 61.5 21.5 58 Dry Weight, lbs 1870.2 4189 14460 6,558 Thrust/Weight
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EngineCycles - Liquid Rocket Engine Cycles AAE 539:...

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